| 摘要 |
PROBLEM TO BE SOLVED: To provide a geared reduction gas turbine engine architecture for enhanced efficiency.SOLUTION: An example gas turbine engine includes, among other things, a geared reduction architecture rotatably coupled to a fan drive shaft, and a high pressure compressor. The gas turbine engine is configured such that a core temperature at an exit of the high-pressure compressor is approximately in a range from about 1150 to about 1350 degrees Fahrenheit at take-off. The gas turbine engine is configured such that an exhaust velocity ratio, defined by the ratio of the fan stream exhaust velocity to the primary stream exhaust velocity, is approximately in a range from about 0.75 to about 0.90. The bypass ratio of the engine is greater than about 8.0. |
